A wing-body combination having a triangular wing of aspect ratio 4 with NACA 0005-63 thickness distribution in streamwise planes, and cambered and twisted for a trapezoidal span load distribution has been investigated at both subsonic and supersonic Mach numbers. The lift, drag, and pitching moment of the model are presented for Mach numbers from 0.25 to 0.96 and 1.20 to 1.70 at a Reynolds number of 1.5 million.